{"id":"F2005L03583","name":"AD/CF6/59 Amdt 1 - HP Compressor Rotor Stage 11-14 Spool Shaft","slug":"ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft","collection":"legislative_instrument","jurisdiction":"commonwealth","status":"in_force","isInForce":true,"actNumber":null,"makingDate":null,"administeringDepartment":null,"currentVersion":{"id":39177,"registerId":"commonwealth-F2005L03583-current","compilationNumber":null,"startDate":"2026-04-01","status":"InForce","reasons":null,"registeredAt":null},"sections":[{"sectionNumber":"General Electric Turbine Engines - CF6 S","sectionType":"division","heading":"General Electric Turbine Engines - CF6 Series","content":"### General Electric Turbine Engines - CF6 Series\n\n| AD/CF6/59 Amdt 1 | HP Compressor Rotor Stage 11-14 Spool Shaft | 13/2005 |\n| ---------------- | ------------------------------------------- | ------- |\n\n| Applicability: | GE CF6-80C2 and CF6-80E1 turbofan engines that have a high pressure compressor rotor (HPCR) stage 11-14 spool shaft with a part number (P/N) listed in Table 1 of the FAA Airworthiness Directive (AD) 2005-17-05 that had a seal wire groove repaired using a circumferential cut at a location specified in Table 2 of FAA AD 2005-17-05.Note 1: The affected stage 11-14 spool shafts are identified by serial number (SN) in the GE service information described in the FAA AD 2005-17-05. These engines are installed on, but not limited to, Airbus Industrie A300, A310, and A330 series airplanes and Boeing 747, 767, and MD-11 series airplanes. |\n| -------------- | ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------- |\n| Requirement:   | Carry out inspection and replacement of spool shaft as detailed in FAA AD2005-17-05.Note 2: FAA AD 2005-17-05 Amendment 39-14226 refers.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                    |\n| Compliance:    | As detailed in FAA AD 2005-17-05 with a revised effective date, unless accomplished earlier.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                |\n|                | This Amendment becomes effective on 22 December 2005.                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                                       |\n| Background:    | This AD requires the inspection of the high pressure compressor rotor (HPCR) stage 11-14 spool shaft for circumferential repair cuts, and to repair or replace the spool shaft if certain circumferential cuts are found.This AD results from an updated stress analysis. The requirements detailed in this AD are to prevent failure of the HPCR stage 11-14 spool shaft due to low-cycle fatigue that could result in an uncontained engine failure.The current amendment of the AD makes the editorial correction in the subject title without changing the technical contents or requirements.                                                          |\n\n|     | The original issue of this Airworthiness Directive becomes effective on24 November 2005. |\n| --- | ---------------------------------------------------------------------------------------- |\n\n![](image.001.png)  \nJames Coyne  \nDelegate of the Civil Aviation Safety Authority\n\n10 November 2005","sortOrder":0},{"sectionNumber":"AD/CF6/59 Amdt 1","sectionType":"part","heading":"AD/CF6/59 Amdt 1","content":"## AD/CF6/59 Amdt 1","sortOrder":1},{"sectionNumber":"HP Compressor Rotor Stage 11-14 Spool Sh","sectionType":"part","heading":"HP Compressor Rotor Stage 11-14 Spool Shaft","content":"## HP Compressor Rotor Stage 11-14 Spool Shaft","sortOrder":2},{"sectionNumber":"13/2005","sectionType":"part","heading":"13/2005","content":"## 13/2005","sortOrder":3}],"analysis":{"flash_summary":{"complexity_score":3,"scope_assessment":{"changed":false,"description":"The amendment is explicitly an editorial correction to the subject title and does not change the technical requirements or expand the population of affected parts. The instrument continues to adopt the inspection and replacement requirements of FAA AD 2005-17-05 and GE service information without substantive change to scope (see Background)."},"complexity_factors":["Short, narrowly focused directive (single safety issue: HPCR stage 11–14 spool shaft circumferential repair cuts).","Direct cross-reference to external normative documents: FAA AD 2005-17-05 (Amendment 39-14226) and GE service information for part numbers and serial numbers.","Limited number of conditional rules: applicability depends on engine model, part number and whether a specific type/location of repair cut was made (tables are in the FAA AD/GE docs).","Requires operators to consult external tables and serial‑number lists (data not contained in this instrument).","Two effective dates noted (original AD effective 24 Nov 2005; this amendment effective 22 Dec 2005) which can cause minor administrative confusion.","Low number of defined terms within the local text, but technical terms (e.g. 'HPCR stage 11–14 spool shaft', 'circumferential repair cut') require cross‑checking with servicing documents."],"plain_english_summary":"**What this instrument does (mechanically)\n\n- Requires owners/operators to inspect certain General Electric CF6-80C2 and CF6-80E1 high‑pressure compressor (HPCR) stage 11–14 spool shafts for circumferential repair cuts, and to repair or replace the spool shaft when cuts meet the criteria in the referenced FAA Airworthiness Directive (FAA AD 2005-17-05). (See: Applicability; Requirement.)\n\n- Adopts the inspection and replacement procedures and compliance times set out in FAA AD 2005-17-05 (Amendment 39-14226) and in GE service information referenced by that FAA AD. The Australian amendment takes effect on 22 December 2005 and notes the original AD became effective on 24 November 2005. (See: Compliance; Requirement.)\n\n- The amendment published here is an editorial correction to the subject title and does not change the technical requirements. (See: Background.)\n\nWho is affected\n\n- Airlines, leasing companies and maintenance organisations that operate or service aircraft fitted with GE CF6-80C2 or CF6-80E1 engines that have an HPCR stage 11–14 spool shaft with a part number listed in Table 1 of FAA AD 2005-17-05 and which previously had a circumferential seal‑wire groove repair cut at locations listed in Table 2 of that FAA AD. The affected spool shaft serial numbers are identified in GE service information referenced by the FAA AD. These engines are installed on (but not limited to) Airbus A300/A310/A330 and Boeing 747/767 and MD-11 aircraft. (See: Applicability.)\n\nWhy it matters (stated purpose and operational effect)\n\n- The stated safety purpose is to mitigate the risk of low‑cycle fatigue leading to HPCR stage 11–14 spool shaft failure and a consequent uncontained engine failure. The instrument achieves this by mandating inspections and removal/repair of shafts that show disallowed circumferential repair cuts. (See: Background; Requirement.)\n\nCosts, incentives, trade‑offs and implementation risks\n\n- Who pays: aircraft operators and their maintenance providers bear the inspection and repair/replacement costs, including parts, labour and any aircraft downtime.\n\n- Supply and timing effects: the requirement may increase near‑term demand for replacement spool shafts and MRO (maintenance, repair and overhaul) capacity; parts lead times can cause schedule disruptions or increased AOG (aircraft on ground) costs.\n\n- Compliance burden: operators must identify affected engine serial numbers (using GE service information and the FAA AD), carry out inspections to the FAA‑specified standard, and document corrective actions. That creates administrative and technical workload for operators and maintenance organisations.\n\n- Implementation risk: correct identification of previously repaired shafts depends on accurate historical records; inspection techniques and judgment calls can produce false positives (leading to possibly unnecessary replacements) or false negatives (missed defects). The regulator relies on the FAA AD and GE service data for technical criteria, reducing domestic rulemaking discretion but increasing dependency on external documents.\n\n- Effects on market participants: independent MRO shops can perform inspections and repairs subject to certification/approval; larger operators may absorb costs more easily than smaller carriers, so cost incidence is uneven.\n\nHow decisions are made and enforced\n\n- The technical requirements and compliance times are those in FAA AD 2005-17-05 and GE service information; the Civil Aviation Safety Authority (CASA) adopts and enforces the requirement domestically. Operators must follow the inspection and corrective actions in the FAA AD and keep compliance records for regulator oversight. (See: Requirement; Compliance.)\n\nReferences to the instrument text\n\n- Key parts of the instrument are labelled in the text as Applicability (which engines and which repaired shafts are affected), Requirement (carry out inspection and replacement as detailed in FAA AD 2005-17-05), Compliance (follow FAA AD with revised effective date), and Background (safety rationale and note that the amendment is editorial). The FAA AD and GE service information contain the detailed part numbers, serial numbers, inspection procedures and acceptance criteria that operators must use.\n\nSummary sentence\n\n- In short: this instrument mandates inspections and required repair/replacement of specific repaired HPCR stage 11–14 spool shafts on GE CF6-80C2 and CF6-80E1 engines, adopting the FAA AD 2005-17-05 technical requirements to prevent spool shaft fatigue failure, and imposes the associated costs and operational impacts on affected operators and maintenance providers."},"kimi_summary":{"content_quality":"ok","complexity_score":3,"scope_assessment":{"changed":false,"description":"This is a minor editorial amendment that corrects the subject title without altering technical content or requirements. The scope remains unchanged from the original AD issued in November 2005."},"complexity_factors":["Heavy reliance on external document: the entire technical requirement is 'as detailed in FAA AD 2005-17-05' — operators must cross-reference a separate US regulation","Narrow, highly technical applicability criteria involving specific part numbers, serial numbers, and repair types that require specialist aviation engineering knowledge to identify","Multiple nested conditions: specific engine models → specific part → specific repair method → specific location of repair","Short document (approximately 300 words) with minimal defined terms, but dense with aviation acronyms (HPCR, P/N, SN, AD)","No internal substantive provisions — the AD functions essentially as a pointer to American regulatory requirements"],"plain_english_summary":"This rule requires airlines, operators and maintenance organisations using GE CF6-80C2 and CF6-80E1 engines (on A300/A310/A330, B747/B767 and MD‑11 types) to inspect—and if necessary replace—the high‑pressure compressor rotor stage 11–14 spool shaft when it has had a circumferential cut repair, following FAA AD 2005‑17‑05. It prevents uncontained engine failure from low‑cycle fatigue. This notice is an editorial amendment (title wording corrected); compliance was due by 22 December 2005."},"flash_summary_failed":{"failed":true,"reason":"A positive credit balance is required for all requests, including BYOK, so fallback providers remain available. Add credits at https://vercel.com/d?to=%2F%5Bteam%5D%2F%7E%2Fai%3Fmodal%3Dtop-up to continue.","source":"analysis-cron"}},"importantCases":[],"_links":{"self":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft","history":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft/history","analysis":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft/analysis","conflicts":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft/conflicts","importantCases":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft/important-cases","documents":"/api/acts/ad-cf6-59-amdt-1-hp-compressor-rotor-stage-11-14-spool-shaft/documents"}}